vehicle dimensions, materials, and justifications static stability margin plan for vehicle safety...

Atomic Aggies

Vehicle dimensions, materials, and justifications Static stability margin Plan for vehicle safety verification and testing Baseline motor selection and justification Thrust-to-weight ratio and rail exit velocity Launch vehicle verification and test plan overview Drawing/Discussion of each major component and

subsystem Baseline payload design Payload

Overview

Main Body: 5.5 inch diameter Blue Tube chosen for strength, price, low weight

Nosecone: Polycarbonate Ogive 1/8” plywood fins chosen for availability of material Overall length: 117.14 inches Approximate Loaded Weight: 34.36 lb.

Vehicle Specifications Team Leader/Vehicle Design: Stacie Benally

Vehicle Design: Valentin Lopez

Static Stability Margin

Atomic Aggies will follow NAR High-Power Rocketry Safety Code.

Proper use of personal protective equipment will be used when handling hazardous materials during construction of the rocket.

Ejection Ground Test will be done before every pre-competition launch.

Safety Checklist will be used to ensure that the rocket is safe to fly.

At least one subscale flight and one full scale flight will be done prior to competition.

SafetySafety Officer: Crystal Escamilla

Manufactory EngineClass/Model

Diameter (mm)

Length (in)

Burn Time (s)

Impulse (N-s)

Avg. thrust(N)

RockSim Altitude (ft.)

Loki L930-LW 75 19.6 4.17 3285 794.6 5600

Motor Selection & Justification

• Motor is flexible for variances in atmospheric conditions

• At breezy winds simulations show 24 oz. of ballast will meet the required altitude of 5280 ft. and at calm wind conditions simulations show 28 oz. of ballast is required to meet the altitude of 5280 ft.

Thrust-to-Weight Ratio & rail exit Velocity

Subscale test launch:◦ Planned launch on November 17

Full scale test launch:◦At least one test launch is planned for January 26◦Combining the data from the full scale launch as well

as the subscale launches we plan on having a flawless competition launch

◦A possible second test launch is planned if needed

Launch, Test Plan Overview

Drogue Parachute: Elliptical Custom 24” diameter Decent Rate: 75 ft/s

Main Parachute: Iris Ultra 96” diameter Decent Rate: 16.53 ft/s

Duel Deployment Recovery SystemCrystal Escamilla & Edgar Gonzalez

Recovery Subsystem Flight Details & Specifications

Apogee Decent/Drogue Decent/Main

Weight (lbs) 25.875 lb 25.875 lb 25.875 lb

Velocity (ft/s) .0164 ft/s 75 ft/s 16.53 ft/s

Kinetic Energy (ft lbf) Section 1 -698.758 ft-lbSection 2 -434.724 ft-lbSection3 -1048.14 ft-lb

Section 1 -27.95 ft-lbSection 2 -17.46 ft-lbSection3 -41.92 ft-lb

24” Drogue parachute Deployments @ Apogee

96” Main Parachute Deployment @ 500ft

Avionics Bay

Payload DesignScientific Design Leader: Jon

PinckleyLayout Leader: Sean Brooks

Payload Integration/Testing

Sensors Controller

DE0-NANO BOARD

Funding Educational Engagement

Project Plan Update

Questions from Panel?